US8402744B2 - Valve system for a gas turbine engine - Google Patents
Valve system for a gas turbine engine Download PDFInfo
- Publication number
- US8402744B2 US8402744B2 US12/053,591 US5359108A US8402744B2 US 8402744 B2 US8402744 B2 US 8402744B2 US 5359108 A US5359108 A US 5359108A US 8402744 B2 US8402744 B2 US 8402744B2
- Authority
- US
- United States
- Prior art keywords
- flow path
- poppet valves
- recited
- actuator system
- valve seat
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related, expires
Links
- 238000001816 cooling Methods 0.000 claims description 12
- 238000002485 combustion reaction Methods 0.000 claims description 5
- 238000000034 method Methods 0.000 claims 6
- 238000012358 sourcing Methods 0.000 claims 3
- 230000008901 benefit Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
- F02K1/30—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for varying effective area of jet pipe or nozzle
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/105—Final actuators by passing part of the fluid
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/38—Introducing air inside the jet
- F02K1/386—Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/40—Use of a multiplicity of similar components
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/50—Control logic embodiments
- F05D2270/52—Control logic embodiments by electrical means, e.g. relays or switches
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/50—Control logic embodiments
- F05D2270/56—Control logic embodiments by hydraulic means, e.g. hydraulic valves within a hydraulic circuit
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/50—Control logic embodiments
- F05D2270/58—Control logic embodiments by mechanical means, e.g. levers, gears or cams
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/60—Control system actuates means
- F05D2270/62—Electrical actuators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/60—Control system actuates means
- F05D2270/64—Hydraulic actuators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/60—Control system actuates means
- F05D2270/66—Mechanical actuators
Definitions
- the present invention relates to a gas turbine engine, and more particularly to a valve system for operation therewith.
- a gas turbine engine such as a turbofan engine for an aircraft, includes a fan section, a compression section, a combustion section, and a turbine section.
- An axis of the engine is centrally disposed within the engine, and extends longitudinally through these sections.
- a primary flow path extends axially through the engine.
- An annular secondary flow path is generally located radially outward of the primary flow path.
- Cooling air along the secondary flow path is often communicated to the primary flow path during particular operating conditions. In order to assure efficient engine operation and performance, communication of the cooling air from the secondary flow path to the primary flow path needs to be meticulously rationed.
- a valve system is located intermediate a secondary flow path and a primary exhaust flow path.
- the valve system selectively communicates secondary airflow to control airflow from a higher pressure plenum into a lower pressure flowpath.
- the valve system generally includes a multiple of poppet valves which are each movably mounted relative to a valve seat for movement between a closed position and an open position.
- the valve seat may be mounted to, or form a portion of, a plenum wall such as an inner cooling liner structure of a gas turbine engine to provide for communication between the secondary flow path and the primary flow path.
- An actuator system having a mechanical, hydraulic, pneumatic or electromagnetic actuator controls movement of the multiple of poppet valves.
- FIG. 1 is a general sectional view an exemplary gas turbine engine embodiment for use with the present invention
- FIG. 2 is an expanded view of a valve system for use with a gas turbine engine
- FIG. 3 is an expanded view of another valve system for use with the gas turbine engine.
- FIG. 1 schematically illustrates a gas turbine engine 10 which generally includes a fan section 12 , a compressor section 14 , a combustor section 16 , a turbine section 18 , an augmentor section 19 , and a nozzle section 20 .
- the compressor section 14 , combustor section 16 , and turbine section 18 are generally referred to as the core engine.
- An axis of the engine A is centrally disposed and extends longitudinally through these sections.
- An engine duct structure 22 and an inner cooling liner structure 24 define an annular secondary flow path 26 at least partially around a perimeter of a primary flow path 28 which directs a primary combustion core gas exhaust flow (illustrated schematically by arrow E). It should be understood that the engine duct structure 22 may also at least partially define various airflow paths other than the disclosed secondary flow path 26 .
- the secondary flow path 26 guides a secondary airflow C between the engine duct structure 22 and the inner cooling liner structure 24 .
- the secondary airflow as defined herein may be any airflow different from the primary combustion core gas exhaust flow E such as an advent cycle third stream fan flow which may be sourced from the fan section 12 and/or compressor section 14 .
- the secondary airflow C is utilized for a multiple of purposes including, for example, cooling, pressurization, partial shielding and mixing with the core gas flow E in the nozzle section 20 during particular operational profiles.
- a valve system 30 is located intermediate the secondary flow path 26 and the primary flow path 28 to selectively communicate secondary airflow C into the primary gas flow path E. For example only, under certain conditions, such as when an aircraft is hovering, less secondary airflow may be required in the nozzle section 20 . By blocking the secondary airflow thereto, additional secondary airflow then becomes available for other purposes. It should be understood that the valve system 30 may be utilized in any location and any environment to control airflow injected from a higher pressure plenum into a lower pressure flowpath such as, for example only, in a nozzle section of a gas turbine engine. The valve system 30 operates rapidly and repeatedly while configured to be received within minimal package space.
- the valve system 30 generally includes a multiple of poppet valves 32 which are each movably mounted to a valve seat 34 for movement between a closed position and an open position along a respective valve axis V.
- the multiple of poppet valves 32 although illustrated as generally round in the disclosed embodiment may be of any shape or configuration. Furthermore, each of the multiple of poppet valves 32 need not be of the same shape or size.
- the valve seat 34 may be mounted to, or form a portion of, a plenum wall such as the inner cooling liner structure 24 (also illustrated in FIG. 1 ) to provide for communication between the secondary flow path 26 and the primary flow path 28 .
- the valve seat 34 at least partially surrounds an airflow path 35 which directs the airflow between the secondary flow path 26 and the primary flow path 28 .
- the airflow path 35 may include a mesh, grid, metering hole, honeycomb structure, or such like which directs and smoothes the airflow therethrough as well as reduces noise generation.
- An actuator system 36 drives a mechanical, hydraulic, pneumatic or electromagnetic actuator 38 which drives movement of each of the multiple of poppet valves 32 in response to a control.
- the actuator system 36 may include a seal structure 42 which may be located at the engine duct structure 22 such that at least a portion of the actuator system 36 may be located external to the engine duct structure 22 . It should be understood that various actuator systems may be usable with the present invention.
- valve system 30 A includes a multiple of poppet valves 32 A movable between a closed position and a multiple of open positions through an actuator system 44 .
- the actuator system 44 in the disclosed embodiment includes a cam structure 46 which opens each of the multiple of poppet valves 32 in response to a drive system 48 .
- the cam structure 46 may be arranged to open the multiple of poppet valves 32 in a sequence which communicates a predetermined volume of airflow relative to the predetermined sequence. It should be understood that essentially infinite sequences may be provided.
- each of the multiple of poppet valves 32 may be individually operated through independent cam linkages or other such linkages.
- Each of the multiple of poppet valves may be of equivalent or different size to control airflow therethrough. It should be understood that other opening sequences and drive arrangements may alternatively or additionally be provided.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Lift Valve (AREA)
Abstract
Description
Claims (22)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
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US12/053,591 US8402744B2 (en) | 2008-03-22 | 2008-03-22 | Valve system for a gas turbine engine |
US12/871,024 US8578716B2 (en) | 2008-03-22 | 2010-08-30 | Valve system for a gas turbine engine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/053,591 US8402744B2 (en) | 2008-03-22 | 2008-03-22 | Valve system for a gas turbine engine |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/053,595 Continuation-In-Part US8240126B2 (en) | 2008-03-22 | 2008-03-22 | Valve system for a gas turbine engine |
Publications (2)
Publication Number | Publication Date |
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US20090235642A1 US20090235642A1 (en) | 2009-09-24 |
US8402744B2 true US8402744B2 (en) | 2013-03-26 |
Family
ID=41087534
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/053,591 Expired - Fee Related US8402744B2 (en) | 2008-03-22 | 2008-03-22 | Valve system for a gas turbine engine |
Country Status (1)
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US (1) | US8402744B2 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10760426B2 (en) | 2017-06-13 | 2020-09-01 | General Electric Company | Turbine engine with variable effective throat |
Citations (43)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4570668A (en) | 1984-01-16 | 1986-02-18 | Parker-Hannifin Corporation | Flow dividing valve |
US4674951A (en) | 1984-09-06 | 1987-06-23 | Societe Nationale D'Etude et de Construction de Meteur D'Aviation (S.N.E.C.M.A.) | Ring structure and compressor blow-off arrangement comprising said ring |
US4679982A (en) | 1984-09-06 | 1987-07-14 | Societe Nationale D'etude Et De Construction De Moteur D'aviation "S. N. E. C. M. A." | Compressor blow-off arrangement |
US4711084A (en) | 1981-11-05 | 1987-12-08 | Avco Corporation | Ejector assisted compressor bleed |
US4854127A (en) | 1988-01-14 | 1989-08-08 | General Electric Company | Bimodal swirler injector for a gas turbine combustor |
US4926633A (en) * | 1989-06-27 | 1990-05-22 | The United States Of America As Represented By The Secretary Of The Air Force | Coolant pressure regulating apparatus |
US5012639A (en) | 1989-01-23 | 1991-05-07 | United Technologies Corporation | Buffer region for the nacelle of a gas turbine engine |
US5123240A (en) | 1990-03-19 | 1992-06-23 | General Electric Co. | Method and apparatus for ejecting foreign matter from the primary flow path of a gas turbine engine |
US5127222A (en) | 1989-01-23 | 1992-07-07 | United Technologies Corporation | Buffer region for the nacelle of a gas turbine engine |
US5211007A (en) | 1991-04-10 | 1993-05-18 | General Electric Company | Method of pressure-ratio control of gas turbine engine |
US5307624A (en) | 1990-04-04 | 1994-05-03 | General Electric Company | Variable area bypass valve assembly |
US5309710A (en) * | 1992-11-20 | 1994-05-10 | General Electric Company | Gas turbine combustor having poppet valves for air distribution control |
US5867980A (en) | 1996-12-17 | 1999-02-09 | General Electric Company | Turbofan engine with a low pressure turbine driven supercharger in a bypass duct operated by a fuel rich combustor and an afterburner |
US6301877B1 (en) | 1995-11-13 | 2001-10-16 | United Technologies Corporation | Ejector extension cooling for exhaust nozzle |
US6385959B1 (en) | 1999-08-24 | 2002-05-14 | MONTOYA CéSAR AGUILERA | Gas turbine engine with increased fuel efficiency and method for accomplishing the same |
US6471475B1 (en) | 2000-07-14 | 2002-10-29 | Pratt & Whitney Canada Corp. | Integrated duct diffuser |
US6588195B2 (en) * | 1999-12-10 | 2003-07-08 | Rolls-Royce Deutschland Ltd & Co Kg | Bleed valve of a compressor, in particular a compressor of a bypass aero-engine |
US20030126853A1 (en) | 2001-12-21 | 2003-07-10 | Koshoffer John Michael | Methods and apparatus for operating gas turbine engines |
US6622475B2 (en) | 2001-04-12 | 2003-09-23 | Snecma Moteurs | Bleed system driven in simplified manner for a turbojet or turboprop engine |
US20030217552A1 (en) | 2002-05-21 | 2003-11-27 | Max Calabro | Engine with a central spike for a space launcher |
US20040006969A1 (en) | 2002-03-12 | 2004-01-15 | Whurr John R. | Variable area nozzle |
US6679048B1 (en) | 2000-10-24 | 2004-01-20 | Lockheed Martin Corporation | Apparatus and method for controlling primary fluid flow using secondary fluid flow injection |
US6694723B2 (en) | 2002-03-27 | 2004-02-24 | United Technologies Corporation | Valve assembly for gas turbine engine |
US6701715B2 (en) | 2002-05-02 | 2004-03-09 | Honeywell International, Inc. | Variable geometry ejector for a bleed air system using integral ejector exit pressure feedback |
US20040187474A1 (en) | 2003-03-31 | 2004-09-30 | Steven Martens | Methods and apparatus for operating gas turbine engines |
US6802691B2 (en) | 2002-11-19 | 2004-10-12 | United Technologies Corporation | Maintainable compressor stability bleed system |
US20040216444A1 (en) | 2003-04-30 | 2004-11-04 | Lovett Jeffery A. | Augmentor |
US6877306B2 (en) | 2003-02-07 | 2005-04-12 | Woodward Governor Company | Nozzle assembly with flow divider and ecology valve |
US20050081509A1 (en) | 2003-10-20 | 2005-04-21 | Johnson James E. | Flade gas turbine engine with fixed geometry inlet |
US20050091982A1 (en) | 2003-10-31 | 2005-05-05 | Renggli Bernard J. | Methods and apparatus for flade engine nozzle |
US6895756B2 (en) | 2002-09-13 | 2005-05-24 | The Boeing Company | Compact swirl augmented afterburners for gas turbine engines |
US6907724B2 (en) | 2002-09-13 | 2005-06-21 | The Boeing Company | Combined cycle engines incorporating swirl augmented combustion for reduced volume and weight and improved performance |
US20050172611A1 (en) | 2004-02-09 | 2005-08-11 | James Blodgett Keith E. | Sinuous chevron exhaust nozzle |
US6997676B2 (en) | 2004-03-10 | 2006-02-14 | General Electric Company | Bifurcated outlet guide vanes |
US7028484B2 (en) | 2002-08-30 | 2006-04-18 | Pratt & Whitney Canada Corp. | Nested channel ducts for nozzle construction and the like |
US7032835B2 (en) | 2004-01-28 | 2006-04-25 | United Technologies Corporation | Convergent/divergent nozzle with modulated cooling |
US7055303B2 (en) | 2003-12-22 | 2006-06-06 | Pratt & Whitney Canada Corp. | Gas turbine engine architecture |
US7114519B2 (en) | 2002-12-18 | 2006-10-03 | Pratt & Whitney Canada Corp. | Normally open reverse flow flapper valve |
US7174704B2 (en) | 2004-07-23 | 2007-02-13 | General Electric Company | Split shroud exhaust nozzle |
US7189055B2 (en) | 2005-05-31 | 2007-03-13 | Pratt & Whitney Canada Corp. | Coverplate deflectors for redirecting a fluid flow |
US7225623B2 (en) | 2005-08-23 | 2007-06-05 | General Electric Company | Trapped vortex cavity afterburner |
US7244104B2 (en) | 2005-05-31 | 2007-07-17 | Pratt & Whitney Canada Corp. | Deflectors for controlling entry of fluid leakage into the working fluid flowpath of a gas turbine engine |
US7500347B2 (en) * | 2003-08-16 | 2009-03-10 | Rolls-Royce Plc | Variable geometry combustor |
-
2008
- 2008-03-22 US US12/053,591 patent/US8402744B2/en not_active Expired - Fee Related
Patent Citations (44)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4711084A (en) | 1981-11-05 | 1987-12-08 | Avco Corporation | Ejector assisted compressor bleed |
US4570668A (en) | 1984-01-16 | 1986-02-18 | Parker-Hannifin Corporation | Flow dividing valve |
US4674951A (en) | 1984-09-06 | 1987-06-23 | Societe Nationale D'Etude et de Construction de Meteur D'Aviation (S.N.E.C.M.A.) | Ring structure and compressor blow-off arrangement comprising said ring |
US4679982A (en) | 1984-09-06 | 1987-07-14 | Societe Nationale D'etude Et De Construction De Moteur D'aviation "S. N. E. C. M. A." | Compressor blow-off arrangement |
US4854127A (en) | 1988-01-14 | 1989-08-08 | General Electric Company | Bimodal swirler injector for a gas turbine combustor |
US5012639A (en) | 1989-01-23 | 1991-05-07 | United Technologies Corporation | Buffer region for the nacelle of a gas turbine engine |
US5127222A (en) | 1989-01-23 | 1992-07-07 | United Technologies Corporation | Buffer region for the nacelle of a gas turbine engine |
US4926633A (en) * | 1989-06-27 | 1990-05-22 | The United States Of America As Represented By The Secretary Of The Air Force | Coolant pressure regulating apparatus |
US5123240A (en) | 1990-03-19 | 1992-06-23 | General Electric Co. | Method and apparatus for ejecting foreign matter from the primary flow path of a gas turbine engine |
US5307624A (en) | 1990-04-04 | 1994-05-03 | General Electric Company | Variable area bypass valve assembly |
US5211007A (en) | 1991-04-10 | 1993-05-18 | General Electric Company | Method of pressure-ratio control of gas turbine engine |
US5309710A (en) * | 1992-11-20 | 1994-05-10 | General Electric Company | Gas turbine combustor having poppet valves for air distribution control |
US6301877B1 (en) | 1995-11-13 | 2001-10-16 | United Technologies Corporation | Ejector extension cooling for exhaust nozzle |
US5867980A (en) | 1996-12-17 | 1999-02-09 | General Electric Company | Turbofan engine with a low pressure turbine driven supercharger in a bypass duct operated by a fuel rich combustor and an afterburner |
US6385959B1 (en) | 1999-08-24 | 2002-05-14 | MONTOYA CéSAR AGUILERA | Gas turbine engine with increased fuel efficiency and method for accomplishing the same |
US6588195B2 (en) * | 1999-12-10 | 2003-07-08 | Rolls-Royce Deutschland Ltd & Co Kg | Bleed valve of a compressor, in particular a compressor of a bypass aero-engine |
US6471475B1 (en) | 2000-07-14 | 2002-10-29 | Pratt & Whitney Canada Corp. | Integrated duct diffuser |
US6679048B1 (en) | 2000-10-24 | 2004-01-20 | Lockheed Martin Corporation | Apparatus and method for controlling primary fluid flow using secondary fluid flow injection |
US6622475B2 (en) | 2001-04-12 | 2003-09-23 | Snecma Moteurs | Bleed system driven in simplified manner for a turbojet or turboprop engine |
US20030126853A1 (en) | 2001-12-21 | 2003-07-10 | Koshoffer John Michael | Methods and apparatus for operating gas turbine engines |
US20040006969A1 (en) | 2002-03-12 | 2004-01-15 | Whurr John R. | Variable area nozzle |
US6694723B2 (en) | 2002-03-27 | 2004-02-24 | United Technologies Corporation | Valve assembly for gas turbine engine |
US6701715B2 (en) | 2002-05-02 | 2004-03-09 | Honeywell International, Inc. | Variable geometry ejector for a bleed air system using integral ejector exit pressure feedback |
US20030217552A1 (en) | 2002-05-21 | 2003-11-27 | Max Calabro | Engine with a central spike for a space launcher |
US7028484B2 (en) | 2002-08-30 | 2006-04-18 | Pratt & Whitney Canada Corp. | Nested channel ducts for nozzle construction and the like |
US6907724B2 (en) | 2002-09-13 | 2005-06-21 | The Boeing Company | Combined cycle engines incorporating swirl augmented combustion for reduced volume and weight and improved performance |
US6895756B2 (en) | 2002-09-13 | 2005-05-24 | The Boeing Company | Compact swirl augmented afterburners for gas turbine engines |
US6802691B2 (en) | 2002-11-19 | 2004-10-12 | United Technologies Corporation | Maintainable compressor stability bleed system |
US7114519B2 (en) | 2002-12-18 | 2006-10-03 | Pratt & Whitney Canada Corp. | Normally open reverse flow flapper valve |
US6877306B2 (en) | 2003-02-07 | 2005-04-12 | Woodward Governor Company | Nozzle assembly with flow divider and ecology valve |
US20040187474A1 (en) | 2003-03-31 | 2004-09-30 | Steven Martens | Methods and apparatus for operating gas turbine engines |
US7093442B2 (en) | 2003-04-30 | 2006-08-22 | United Technologies Corporation | Augmentor |
US20040216444A1 (en) | 2003-04-30 | 2004-11-04 | Lovett Jeffery A. | Augmentor |
US7500347B2 (en) * | 2003-08-16 | 2009-03-10 | Rolls-Royce Plc | Variable geometry combustor |
US20050081509A1 (en) | 2003-10-20 | 2005-04-21 | Johnson James E. | Flade gas turbine engine with fixed geometry inlet |
US20050091982A1 (en) | 2003-10-31 | 2005-05-05 | Renggli Bernard J. | Methods and apparatus for flade engine nozzle |
US7055303B2 (en) | 2003-12-22 | 2006-06-06 | Pratt & Whitney Canada Corp. | Gas turbine engine architecture |
US7032835B2 (en) | 2004-01-28 | 2006-04-25 | United Technologies Corporation | Convergent/divergent nozzle with modulated cooling |
US20050172611A1 (en) | 2004-02-09 | 2005-08-11 | James Blodgett Keith E. | Sinuous chevron exhaust nozzle |
US6997676B2 (en) | 2004-03-10 | 2006-02-14 | General Electric Company | Bifurcated outlet guide vanes |
US7174704B2 (en) | 2004-07-23 | 2007-02-13 | General Electric Company | Split shroud exhaust nozzle |
US7189055B2 (en) | 2005-05-31 | 2007-03-13 | Pratt & Whitney Canada Corp. | Coverplate deflectors for redirecting a fluid flow |
US7244104B2 (en) | 2005-05-31 | 2007-07-17 | Pratt & Whitney Canada Corp. | Deflectors for controlling entry of fluid leakage into the working fluid flowpath of a gas turbine engine |
US7225623B2 (en) | 2005-08-23 | 2007-06-05 | General Electric Company | Trapped vortex cavity afterburner |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10760426B2 (en) | 2017-06-13 | 2020-09-01 | General Electric Company | Turbine engine with variable effective throat |
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